Author : Sturat L. Treon
Publisher :
Page : 26 pages
File Size : 31,95 MB
Release : 1957
Category :
ISBN :
Author : Earl D. Knechtel
Publisher :
Page : 36 pages
File Size : 12,21 MB
Release : 1956
Category : Charts, diagrams, etc
ISBN :
An experimental investigation was conducted to determine the longitudinal aerodynamic characteristics at transonic speeds of missile configurations having three blunted cone-cylinder bodies. Modifications of the basic model were tested to indicate the effects of (a) relative lengths of coplanar bodies, (b) seals between the cylindrical portions of the bodies, (c) horizontal connecting surfaces near the rear of the bodies, and (d) triangular rather than coplanar body grouping. Lift, drag, and pitching-moment data were obtained at angles of attack from -4 to 12 degrees and Mach numbers from 0.6 to 1.4 for a constant Reynolds number of 5,500,000, based on average body length.
Author : United States. National Aeronautics and Space Administration
Publisher :
Page : pages
File Size : 43,77 MB
Release : 1960-07
Category :
ISBN :
Author : William J. Monta
Publisher :
Page : 36 pages
File Size : 12,24 MB
Release : 1971
Category : Aerodynamics
ISBN :
Author : M. Leroy Spearman
Publisher :
Page : 36 pages
File Size : 10,22 MB
Release : 1977
Category : Aerodynamics
ISBN :
Author : M. Leroy Spearman
Publisher :
Page : 34 pages
File Size : 46,60 MB
Release : 1977
Category : Aerodynamics
ISBN :
Author : James F. Campbell
Publisher :
Page : 44 pages
File Size : 44,4 MB
Release : 1967
Category : Aerodynamics
ISBN :
Author :
Publisher :
Page : 456 pages
File Size : 28,38 MB
Release : 1966
Category : Aeronautics
ISBN :
Author : Edward F. Ulmann
Publisher :
Page : 34 pages
File Size : 11,9 MB
Release : 1954
Category : Ballistic missiles
ISBN :
Tests were conducted at Mach number 4.05 to determine the aerodynamic characteristics of several missile models having turbulent boundary layers and to compare these results with available method of predicting the aerodynamic characteristics. (The condition of the boundary layer was determined by the china-clay-lacquer boundary-layer-visualization technique.) Normal force and pitching moment were measured through an angle-of-attack range of 0 to between 4 and 8 degrees, depending upon balance limitations, and at roll angles of 0 and 45 degrees; drag was measured only at 0 degrees angle of attack.
Author : Jimmie N. Derrick
Publisher :
Page : 896 pages
File Size : 19,13 MB
Release : 1976
Category : Aerodynamics, Transonic
ISBN :
Wind tunnel tests were conducted in a 16 ft. transonic tunnel, a supersonic tunnel, A and a trisonic tunnel to establish a bank of systematic data for body and body-tail configurations at high angles of attack. The configurations were tested at Mach numbers between 0.8 and 3.0, angles of attack from -2 to 45 degrees, and roll angles from 0 to 90 degrees. The aerodynamic characteristics were obtained for the total configuration as well as each of the four undeflected tail fins.
